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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
 ACTION: Notice of proposed rulemaking (NPRM).
 SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A300-600 series airplanes. The existing AD currently requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. The existing AD also provides for optional terminating action for certain inspections. This proposed AD would retain all requirements of the existing AD, mandate the previously optional terminating action, reduce the applicability of the existing AD, and add repetitive inspections behind scuff plates for certain affected airplanes. This proposed AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are proposing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings.
 DATES: We must receive comments on this proposed AD by February 20, 2007.
 ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. *DOT Docket Web site:*
                         Go to 
                        *http://dms.dot.gov*
                         and follow the instructions for sending your comments electronically.
                    *Government-wide rulemaking Web site:*
                         Go to 
                        *http://www.regulations.gov*
                         and follow the instructions for sending your comments electronically.
                    *Mail:*
                         Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, Washington, DC 20590.
                    *Fax:*
                         (202) 493-2251.
                    *Hand Delivery:*
                         Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD.
 FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.


SUPPLEMENTARY INFORMATION: ( print page 2470) Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the 
                    **ADDRESSES**
                     section. Include the docket number “Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to 
                    *http://dms.dot.gov*, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the 
                    **Federal Register**
                     published on April 11, 2000 (65 FR 19477-78), or you may visit 
                    *http://dms.dot.gov.* Examining the Docket You may examine the AD docket on the Internet at 
                    *http://dms.dot.gov*, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the 
                    **ADDRESSES**
                     section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On July 24, 1998, we issued AD 98-16-05, amendment 39-10680 (63 FR 40812, July 31, 1998), for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes). That AD requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also provides for optional terminating action for certain inspections. That AD resulted from reports indicating that corrosion was found behind the scruff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. We issued that AD to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings. Other Relevant Rulemaking We have previously issued AD 97-11-03, amendment 39-10032 (62 FR 28325, May 23, 1997), applicable to all Airbus Model A300 series airplanes. That AD requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also requires modification of the passenger/crew door frames, which terminates certain inspections. We also previously issued AD 98-16-06, amendment 39-10682 (63 FR 40819, July 31, 1998), for all Airbus Model A310 series airplanes. That AD requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also provides for optional terminating action for certain inspections. We are considering further rulemaking to mandate the optional terminating action. Actions Since Existing AD Was Issued Since we issued AD 98-16-05, the Direction Générale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, issued French airworthiness directives 1991-132-124(B) R1, dated November 29, 2000 (to replace French airworthiness directive 91-132-124(B), dated June 26, 1991, which is referred to in AD 98-16-05), and F-2004-103, dated July 7, 2004. The DGAC advises that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings on certain Airbus Model A300-600 series airplanes and to remove certain airplanes from the applicability of the existing AD that are no longer subject to the existing requirements. Corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, if not corrected, could result in reduced structural integrity of the door surroundings. After the DGAC issued French airworthiness directive 1991-132-124(B) R1 on November 29, 2000, we determined at that time that further rulemaking was not necessary, because the changes to AD 98-16-05 would be relieving in nature. However, since French airworthiness directive F-2004-103 mandates the previously optional modification, we now agree with the DGAC that further rulemaking is indeed necessary to improve the fatigue behavior of the cabin door surroundings, and this proposed AD follows from that determination. Relevant Service Information Airbus has issued and revised the service bulletins in the following table: Service Bulletins
Airbus Service Bulletin—
Describes procedures for—A300-53-6011, Revision 07, dated January 24, 2005 (Revision 3, dated February 4, 1991, of the service bulletin was referenced in AD 98-16-05 as an appropriate source of service information)
Doing initial inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repairing any cracked or corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in Revision 3 of the service bulletin. Revision 07 also revises the effectivity by adding additional airplanes.A300-53-6022, Revision 04, dated January 24, 2005 (the original issue, dated February 4, 1991, of the service bulletin was referenced in AD 98-16-05 as an appropriate source of service information)
Doing repetitive inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repairing any cracked/corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in original issue of the service bulletin. Revision 04 also revises the effectivity by adding additional airplanes.( print page 2471)A300-53-6018, Revision 03, dated July 26, 2006, including Appendix 01 (Revision 1, dated April 29, 1992, of the service bulletin was referenced in AD 98-16-05 as an appropriate source of service information)
Doing repetitive inspections for cracks/corrosion of the holes of the corner doublers, the fail-safe ring, and the door frames of the passenger/crew door structures, and repairing any cracked/corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in Revision 1 of the service bulletin.A300-53-6002, Revision 06, dated May 17, 2004 (Revision 3, dated February 22, 1992, of the service bulletin was referenced in AD 98-16-05 as an appropriate source of service information)
Modifying the passenger/crew door structures, which ends the repetitive inspections of the holes of the corner doublers specified in Airbus Service Bulletin A300-53-6018, the fail-safe ring, and the door frames for certain airplanes. The modification includes cold expansion of fastener holes; a ROTO test; repair of any crack; repair of any crack that cannot be eliminated per Airbus; installation of new oversize fasteners and modified brackets; and installation of an additional steel doubler. The modification is essentially identical to that specified in Revision 3 of the service bulletin.
 Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information to ensure the continued airworthiness of these airplanes in France. FAA's Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC's findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 98-16-05, retain the requirements of the existing AD, mandate the previously optional terminating action, reduce the applicability of the existing AD, and add repetitive inspections behind scuff plates for certain affected airplanes. This proposed AD would also require accomplishing the actions specified in service information described previously. Difference Between French Airworthiness Directive and This Proposed AD The applicability of French airworthiness directive 1991-132-124(B) R1 excludes Airbus Model A300-600 series airplanes on which Airbus Service Bulletin A300-53-6002, Revision 2, dated May 6, 1991 (or any other later approved revision), has been accomplished in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD includes a requirement to accomplish the actions specified in Revision 06 of that service bulletin. This requirement would ensure that the actions specified in the service bulletin and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. The service bulletins specify to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the European Aviation Safety Agency (EASA) (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the EASA approve would be acceptable for compliance with this proposed AD. Change to Existing AD This proposed AD would retain all requirements of AD 98-16-05. Since AD 98-16-05 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: Revised Paragraph Identifiers
Requirement in 
                             AD 98-16-05
Corresponding requirements in this proposed ADParagraph (a)
Paragraph (f).Paragraph (b)
Paragraph (g).Paragraph (c)
Paragraph (h).Paragraph (d)
Paragraph (i).Paragraph (e)
paragraph (j).Paragraph (f)
Paragraph (k).Paragraph (g)
Paragraph (l).
 The DGAC revised the applicability of French airworthiness directives 1991-132-124(B) R1 and F-2004-103 to exclude Model A300-600 series airplanes on which Airbus Modification 5068, 6514, 7201, and 7298 have been incorporated in production. Therefore, the applicability of the proposed AD parallels the French airworthiness directives in that regard. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate per work hour is $80. Estimated Costs
Action
Work hours
Parts
Cost per airplane
Number of U.S.-registered airplanes
Fleet costRepetitive inspections behind scuff plates
37
None
$2,960
129
$381,840.Repetitive inspections of corner doublers, fail-safe ring, and door frames
Between 1 and 51
None
Between $80 and $4,080
129
Between $10,320 and $526,320.( print page 2472)Terminating modification for repetitive inspection of corner doublers, fail-safe ring, and door frames
Between 8 and 67, depending on kit purchased
Between $580 and $11,273, depending on kit purchased
Between $1,220 and $16,633
129
Between $157,380 and $2,145,657.
 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the 
                    **ADDRESSES**
                     section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Safety
 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority:
                        49 U.S.C. 106(g), 40113, 44701. § 39.13
  2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39-10680 (63 FR 40812, July 31, 1998) and adding the following new airworthiness directive (AD): **Airbus:**
                                 Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 20, 2007. Affected ADs (b) This AD supersedes AD 98-16-05. Applicability (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; excluding those airplanes on which Airbus Modification 5068, 6514, 7201, and 7298 have been incorporated in production. Unsafe Condition (d) This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 98-16-05 Initial Inspection Behind Scuff Plates and Repair if Necessary (f) Perform an initial inspection of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A300-53-6011, Revision 3, dated February 4, 1991, at the time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If any crack or corrosion is found during this inspection, prior to further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have been accomplished prior to delivery of the airplane: Perform the initial inspection within 9 years since date of manufacture, or within 1 year after September 4, 1998 (the effective date of AD 98-16-05), whichever occurs later. (2) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have not been accomplished; and on which the procedures described in Airbus Service Information Letter (SIL) A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been accomplished: Perform the initial inspection within 5 years after accomplishment of the procedures described in the SIL, or within 1 year after September 4, 1998, whichever occurs later. (3) For airplanes on which Modification 5382S6526 (for forward doors), and Modification 5382D4741 (for all other doors), and the procedures described in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been accomplished: Perform the initial inspection within 4 years since date of manufacture, or within 1 year after September 4, 1998, whichever occurs later. Repetitive Inspections Behind Scuff Plates (g) Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991, at the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishment of these inspections is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. 
                                ( print page 2473) (1) For the forward and mid passenger/crew doors, the bulk cargo door, and the aft passenger/crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler: Perform the first inspection within 5 years after accomplishing the inspection required by paragraph (f) of this AD; and repeat the inspection thereafter at intervals not to exceed 5 years. (2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors: Perform the first inspection within 5 years or 6,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 6,000 landings, whichever occurs first. Repair of Scuff Plates if Necessary (h) If any crack is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD. (i) If corrosion is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraph (i)(1) or (i)(2) of this AD. (1) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors, and for the mid passenger/crew door: Inspect at intervals not to exceed 5 years or 5,000 landings, whichever occurs first. (2) For the forward passenger/crew doors and bulk cargo doors: Inspect at intervals not to exceed 5 years. Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (j) Perform an inspection to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the left- and right-hand forward, mid, and aft passenger/crew door structures, in accordance with Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992, and at the applicable time specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. (1) For the upper corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later. (2) For the lower corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. (3) For the upper and lower corners of the mid doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later. (4) For the upper and lower corners of the aft doors, and for the parts underneath the corners of the upper door frames: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door Frames (k) Repeat the inspections required by paragraph (j) of this AD at the applicable times specified in paragraphs (k)(1), (k)(2), (k)(3), (k)(4), and (k)(5) of this AD. (1) For the upper corners of the forward doors: Inspect at intervals not to exceed 6,000 landings. (2) For the lower corners of the forward doors: Inspect at intervals not to exceed 10,000 landings. (3) For the upper and lower corners of the mid and aft doors on which an inspection required by paragraph (j) of this AD was accomplished using a ROTO test technique: Inspect at intervals not to exceed 8,000 landings. (4) For the upper and lower corners of the mid and aft doors on which an inspection required by paragraph (j) of this AD was accomplished using an X-ray technique: Inspect at intervals not to exceed 3,500 landings. (5) For the areas around the fasteners in the vicinity of stringer 12 on the upper door frames of the aft doors on which an inspection required by paragraph (j) of this AD was accomplished using a visual technique: Inspect at intervals not to exceed 6,900 landings. Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames If Necessary (l) If any crack is found during any inspection required by paragraph (j) or (k) of this AD: Prior to further flight, accomplish the requirement of paragraph (l)(1) or (l)(2) of this AD, as applicable. (1) If any crack is found, and the crack can be eliminated using the method specified in Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992; or Revision 02, excluding Appendix 01, dated November 27, 2000: Prior to further flight, repair the crack in accordance with that service bulletin. (2) If any crack is found, and the crack cannot be eliminated using the method specified in Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. New Requirements of This AD New Revision of Service Bulletins (m) As of the effective date of this AD, use only the applicable service bulletins specified in Table 1 of this AD; except where the service bulletins recommend contacting Airbus for appropriate action, before further flight, repair the cracked part using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Table 1.—New Revision of Service Bulletins
Do the action(s) required by—
In accordance with the Accomplishment Instructions of Airbus Service Bulletin—(1) Paragraph (f) of this AD
A300-53-6011, Revision 07, dated January 24, 2005.(2) Paragraphs (g) through (i) of this AD
A300-53-6022, Revision 04, dated January 24, 2005.(3) Paragraphs (j), (k), and (l)(1) of this AD
A300-53-6018, Revision 03, excluding Appendix 01, dated July 26, 2006.
 Initial Inspection Behind Scuff Plates and Repair If Necessary for Additional Airplanes (n) Perform an initial inspection of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6011, Revision 07, dated January 24, 2005; at the applicable time specified in Table 2 of this AD. If any crack or corrosion is found during this inspection, before further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. 
                                ( print page 2474) Table 2.—Compliance Time Initial Inspection Behind Scuff Plate for Additional Airplanes
For airplanes on which—
And on which—
Compliance time 
                                         (whichever occurs later)Threshold
Grace period(1) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have been done before the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness
None
Within 108 months after first flight
Within 12 months after the effective date of this AD.(2) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have been done before the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness
None
Within 108 months after first flight
Within 12 months after the effective date of this AD.(3) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have not been done before the effective date of this AD
The actions specified in Airbus Service Information Letter (SIL) A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been done
Within 60 months after accomplishing the actions specified in the SIL
Within 12 months after the effective date of this AD.(4) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have not been done before the effective dated of this AD
The actions specified in Airbus SIL A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been done
Within 60 months after accomplishing the actions specified in the SIL
Within 12 months after the effective date of this AD.(5) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have not been done before the effective date of this AD
The actions specified in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been done
Within 48 months since the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness
Within 12 months after the effective date of this AD.(6) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have not been done before the effective date of this AD
The actions specified in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been done
Within 48 months since the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness
Within 12 months after the effective date of this AD.
 Repetitive Inspections behind Scuff Plates for Additional Airplanes (o) For airplanes identified in Table 2 of this AD: Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A300-53-6022, Revision 04, dated January 24, 2005, at the applicable times specified in paragraphs (o)(1) and (o)(2) of this AD. Accomplishment of these inspections is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For the forward and mid passenger/crew doors, the bulk cargo door, and the aft passenger/crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler: Perform the first inspection within 60 months after accomplishing the inspection required by paragraph (n) of this AD; and repeat the inspection thereafter at intervals not to exceed 60 months. (2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors: Perform the first inspection within 60 months or 6,000 landings after accomplishing the inspection required by paragraph (n) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 60 months or 6,000 landings, whichever occurs first. Repair of Scuff Plates If Necessary (p) If any crack is found during any inspection required by paragraph (o) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, Revision 04, dated January 24, 2005. Thereafter, perform the repetitive inspections required by paragraph (o) of this AD at the applicable times specified in paragraphs (o)(1) and (o)(2) of this AD. (q) If corrosion is found during any inspection required by paragraph (o) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, Revision 04, dated January 24, 2005. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraph (q)(1) or (q)(2) of this AD. (1) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors, and for the mid passenger/crew door: Inspect at intervals not to exceed 60 months or 5,000 landings, whichever occurs first. (2) For the forward passenger/crew doors and bulk cargo doors: Inspect at intervals not to exceed 60 months. Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (r) Before the accumulation of 30,000 total flight cycles since the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness, or during the next inspection required by paragraph (k) of this AD, whichever occurs later: Modify the passenger/crew door structures in accordance 
                                ( print page 2475)
                                with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6002, Revision 06, dated May 17, 2004. Accomplishment of this modification constitutes terminating action for the inspections required by paragraphs (j) and (k) of this AD. The inspections required by paragraphs (f) and (n) of this AD, as applicable, must be done before accomplishing this modification. Earlier Revisions of Service Bulletins (s) Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 3 of this AD, are acceptable for compliance with the corresponding requirements of this AD. Table 3.—Earlier Revisions of Service Bulletins
Airbus Service Bulletin
Revision 
                                         level
Date(1) A300-53-6002
03
February 22, 1992.(2) A300-53-6002
4
July 13, 1992.(3) A300-53-6002
05
September 7, 2000.(4) A300-53-6011
04
July 2, 1996.(5) A300-53-6011
05
September 7, 2000.(6) A300-53-6011
06
November 12, 2002.(7) A300-53-6018, excluding Appendix 01
02
November 27, 2000.(8) A300-53-6022
01
July 2, 1996.(9) A300-53-6022
02
September 7, 2000.(10) A300-53-6022
03
November 12, 2002.
 Alternative Methods of Compliance (AMOCs) (t)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously in accordance with AD 98-16-05 are approved as AMOCs for the corresponding provisions of paragraphs (f) through (l) of this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (u) French airworthiness directives 1991-132-124(B) R1, dated November 29, 2000, and F-2004-103, dated July 7, 2004, also address the subject of this AD.
 Issued in Renton, Washington, on January 8, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.


[FR Doc. E7-715 Filed 1-18-07; 8:45 am] BILLING CODE 4910-13-P